The material is air, (Initial conditions) the gauge pressure is 0, the velocity is 0, k is 0.00375, omega is 3.375.
The boundary conditions were:, inlet velocity: x=12 m/s, I indicated the freestream walls, I indicatetd the pressure outlet of 0. I also indicated thet the floor was moving at x=12 m/s. I also created a wall (no-slip) with the wing geometry. After that i just made the results to show only the forces.
The values I would espect would be in [50-90] N of downforce.
Thank you for your help.